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NREL's S821 Airfoil (s821-nr) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NREL's S821 Airfoil (s821-nr)
Reynolds number: 100,000
Max Cl/Cd: 35.61 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s821-nr-100000.txt
Download as CSV file: xf-s821-nr-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S821 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -5.000   0.0314   0.12009   0.11369  -0.0343   0.9595   0.3024
  -4.750   0.0507   0.11779   0.11142  -0.0372   0.9487   0.3070
  -4.500   0.0245   0.11791   0.11147  -0.0421   0.9391   0.3122
  -4.250   0.0715   0.11293   0.10655  -0.0451   0.9313   0.3132
  -4.000   0.1197   0.10873   0.10240  -0.0494   0.9270   0.3149
  -3.750   0.1500   0.10604   0.09977  -0.0511   0.9160   0.3175
  -3.500   0.1854   0.10306   0.09683  -0.0553   0.9105   0.3216
  -3.250   0.1307   0.10590   0.09958  -0.0574   0.8944   0.3303
  -3.000   0.1918   0.09970   0.09344  -0.0618   0.8919   0.3313
  -2.750   0.2321   0.09581   0.08963  -0.0635   0.8821   0.3326
  -2.500   0.2773   0.09209   0.08597  -0.0671   0.8766   0.3347
  -2.250   0.3223   0.08867   0.08259  -0.0719   0.8730   0.3385
  -2.000   0.3433   0.08683   0.08077  -0.0741   0.8621   0.3448
  -1.750   0.3402   0.08541   0.07929  -0.0793   0.8543   0.3508
  -1.500   0.4109   0.08019   0.07412  -0.0863   0.8511   0.3527
  -1.250   0.4470   0.07761   0.07158  -0.0883   0.8372   0.3551
  -1.000   0.5016   0.07428   0.06823  -0.0952   0.8301   0.3598
  -0.750   0.4392   0.07778   0.07162  -0.0933   0.8107   0.3702
  -0.500   0.4963   0.07311   0.06698  -0.0962   0.7987   0.3714
  -0.250   0.5577   0.06932   0.06316  -0.1011   0.7875   0.3736
   0.000   0.5825   0.06784   0.06171  -0.1007   0.7719   0.3763
   0.250   0.6104   0.06637   0.06019  -0.1020   0.7595   0.3806
   0.500   0.5294   0.07052   0.06429  -0.0947   0.7452   0.3911
   0.750   0.5667   0.06714   0.06093  -0.0962   0.7344   0.3923
   1.000   0.6079   0.06451   0.05831  -0.0972   0.7221   0.3938
   1.250   0.6401   0.06286   0.05667  -0.0973   0.7107   0.3963
   1.500   0.6619   0.06182   0.05566  -0.0964   0.6993   0.4001
   1.750   0.6739   0.06122   0.05505  -0.0954   0.6895   0.4064
   2.250   0.4825   0.05099   0.04455  -0.0903   0.6764   0.3500
   2.500   0.4851   0.04312   0.03632  -0.1006   0.6705   0.3497
   2.750   0.4916   0.04604   0.03956  -0.0914   0.6590   0.3509
   3.000   0.5842   0.05281   0.04659  -0.0835   0.6487   0.3659
   3.250   0.5780   0.05152   0.04536  -0.0809   0.6400   0.3629
   3.500   0.5495   0.04609   0.03983  -0.0848   0.6325   0.3564
   3.750   0.5796   0.04270   0.03627  -0.0911   0.6254   0.3597
   4.000   0.6118   0.03618   0.02927  -0.1054   0.6159   0.3711
   4.250   0.6321   0.03624   0.02945  -0.1034   0.6064   0.3733
   4.500   0.6726   0.03625   0.02947  -0.1038   0.5989   0.3764
   4.750   0.6759   0.03630   0.02968  -0.1006   0.5879   0.3795
   5.000   0.7398   0.03386   0.02681  -0.1099   0.5783   0.3916
   5.250   0.7490   0.03414   0.02731  -0.1064   0.5681   0.3942
   5.500   0.7745   0.03414   0.02740  -0.1049   0.5583   0.3978
   5.750   0.8016   0.03407   0.02736  -0.1044   0.5486   0.4028
   6.000   0.8399   0.03303   0.02613  -0.1078   0.5366   0.4124
   6.250   0.8689   0.03277   0.02592  -0.1073   0.5266   0.4171
   6.500   0.8840   0.03288   0.02619  -0.1045   0.5152   0.4212
   6.750   0.9169   0.03263   0.02589  -0.1047   0.5043   0.4284
   7.000   0.9482   0.03203   0.02518  -0.1060   0.4912   0.4375
   7.250   0.9680   0.03202   0.02529  -0.1038   0.4798   0.4418
   7.500   0.9914   0.03187   0.02517  -0.1022   0.4674   0.4477
   7.750   1.0129   0.03175   0.02506  -0.1014   0.4538   0.4562
   8.000   1.0455   0.03130   0.02450  -0.1016   0.4403   0.4636
   8.250   1.0544   0.03137   0.02473  -0.0980   0.4260   0.4685
   8.500   1.0697   0.03136   0.02475  -0.0956   0.4112   0.4754
   8.750   1.0940   0.03112   0.02436  -0.0951   0.3947   0.4847
   9.000   1.1063   0.03107   0.02432  -0.0919   0.3789   0.4898
   9.250   1.1048   0.03127   0.02465  -0.0870   0.3627   0.4950
   9.500   1.1114   0.03154   0.02489  -0.0839   0.3446   0.5022
   9.750   1.1196   0.03195   0.02522  -0.0813   0.3252   0.5094
  10.000   1.1212   0.03259   0.02587  -0.0774   0.3066   0.5144
  10.250   1.1239   0.03341   0.02664  -0.0741   0.2876   0.5207
  10.500   1.1299   0.03441   0.02748  -0.0719   0.2683   0.5287
  10.750   1.1332   0.03553   0.02852  -0.0693   0.2510   0.5345
  11.000   1.1357   0.03682   0.02976  -0.0665   0.2354   0.5404
  11.250   1.1418   0.03823   0.03106  -0.0647   0.2206   0.5481
  11.500   1.1513   0.03970   0.03238  -0.0635   0.2069   0.5563
  11.750   1.1605   0.04104   0.03359  -0.0617   0.1950   0.5629
  12.000   1.1644   0.04273   0.03538  -0.0601   0.1842   0.5706
  12.250   1.1750   0.04438   0.03697  -0.0593   0.1739   0.5794
  12.500   1.1879   0.04572   0.03818  -0.0580   0.1647   0.5873
  12.750   1.1914   0.04769   0.04028  -0.0569   0.1565   0.5961
  13.000   1.2031   0.04931   0.04187  -0.0561   0.1486   0.6047
  13.250   1.2106   0.05105   0.04364  -0.0551   0.1415   0.6134
  13.500   1.2204   0.05309   0.04569  -0.0547   0.1346   0.6238
  13.750   1.2315   0.05461   0.04719  -0.0537   0.1283   0.6330
  14.000   1.2369   0.05704   0.04973  -0.0534   0.1225   0.6437
  14.250   1.2505   0.05849   0.05113  -0.0526   0.1169   0.6539
  14.500   1.2537   0.06118   0.05398  -0.0524   0.1121   0.6648
  14.750   1.2629   0.06300   0.05582  -0.0517   0.1074   0.6755
  15.000   1.2706   0.06556   0.05845  -0.0517   0.1030   0.6883
  15.250   1.2714   0.06813   0.06120  -0.0512   0.0992   0.6984
  15.500   1.2894   0.06974   0.06272  -0.0508   0.0951   0.7140
  15.750   1.2804   0.07349   0.06676  -0.0509   0.0922   0.7245
  16.000   1.2896   0.07549   0.06877  -0.0506   0.0889   0.7400
  16.250   1.2941   0.07833   0.07171  -0.0506   0.0861   0.7557
  16.500   1.2831   0.08267   0.07635  -0.0513   0.0840   0.7687
  16.750   1.2836   0.08561   0.07941  -0.0515   0.0816   0.7868
  17.000   1.3001   0.08674   0.08049  -0.0503   0.0790   0.8157
  17.250   1.2733   0.09288   0.08706  -0.0523   0.0780   0.8297
  17.500   1.2477   0.09892   0.09350  -0.0543   0.0769   0.8487
  17.750   1.2200   0.10443   0.09938  -0.0554   0.0761   0.8884
  18.000   1.1942   0.11091   0.10615  -0.0590   0.0751   1.0000
  18.250   1.2480   0.10921   0.10395  -0.0587   0.0719   1.0000
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